This paper presents the study of subsonic intake, integrated with curvilinear fuselage fore body. Intake's complex shape leads to the formation of longitudinal vortices causing a significant uneven distribution of flow parameters at the output section of the intake. Numerical research, using ESI RANS and RANS / ILES methods, of air intake flow were obtain at different throttle modes. The flow fields were compare with the experimental results. Throttling modes with pronounced unevenness at the output section were determined. By means of RANS/ILES methods conducted study of a flow control with synthetic jets in the subsonic intake. The jet's parameters, which made it possible to reduce the circumferential unevenness by 5 ÷ 39 % at the output section of the intake, were determined.
This paper presents the results of numerical and experimental study of subsonic intake, integrated with curvilinear fuselage fore body under subsonic flowing. Numerical research of air intake flow and performance were obtained at different throttle modes and turbulence models at flight altitude H = 0 ÷ 0.5 km and Mach number M = 0.4. An experimental research was performed in wind tunnel of Central Institute of Aviation Motors at M = 0.4, an attack angle = 0 and Reynolds number Re = 1.8 × 10 6. The losses of total pressure at the different throttle modes, distribution of the static pressure along the intake and fuselage length were determined. Satisfactory agreement between calculated and experimental data was obtained. A flow control air intake methods are proposed.
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